CN102806992B - There is the revolve inclination sensor of gimbal attachment arrangement - Google Patents
There is the revolve inclination sensor of gimbal attachment arrangement Download PDFInfo
- Publication number
- CN102806992B CN102806992B CN201210178028.5A CN201210178028A CN102806992B CN 102806992 B CN102806992 B CN 102806992B CN 201210178028 A CN201210178028 A CN 201210178028A CN 102806992 B CN102806992 B CN 102806992B
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- Prior art keywords
- pivotal arm
- pivot
- axle
- motion
- attached
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- 238000000034 method Methods 0.000 claims description 5
- 230000000712 assembly Effects 0.000 claims 4
- 238000000429 assembly Methods 0.000 claims 4
- 230000007246 mechanism Effects 0.000 abstract description 15
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0005—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0005—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
- B64D2045/001—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear for indicating symmetry of flaps deflection
Abstract
The present invention relates to the revolve inclination sensor with gimbal attachment arrangement.Comprise a sensing device for the sensor module detected disclosed in wing flaps position and motion, it produces the signal corresponding to flap configuration.Sensor module comprise be attached to moveable wing flap, for mechanically by the motion UNICOM of wing flap to the connecting rod mechanism of sensing device.Connecting rod mechanism comprises the first pivot and the second pivot, first pivotal mounting to wing flap and around first axle arrange, the second pivot is attached to the first pivot, for the motion around the second axis transverse to first axle.
Description
Technical field
The disclosure relates in general to the sensor device for determining moveable wing flaps position.Especially, the disclosure relates to the motion of translation of extension and the sensor device of rotary motion that adapt to wing flaps.
Background technology
Aircraft comprises the wing with removable wing flap, thinks that the flight operation of expectation specifically arranges pneumatic wing performance.Utilize actuator to move wing flap, this actuator drives wing flap to desired position.It should be appreciated that the control of Chinese-style jacket with buttons down the front wing member needs to understand the position when front flap.The information relevant to flap configuration is obtained by using sensor.Sensor is installed into the motion of some part measuring the flap-actuating mechanism representing flap configuration.Therefore, require that sensor mechanism is installed in wing, and the total movement of wing flap must be adapted to.
Summary of the invention
Comprise sensing device for the sensor module detected disclosed in the motion of wing flaps and position, it produces the signal of the position corresponding to wing flap.Sensor module comprises connecting rod mechanism, and it is connected to moveable wing flap, for mechanically by the motion UNICOM of wing flap to sensing device.The sensor module of example adapts to wing flap from retracted position to the linear component of the motion of extended position and rotational component.
Connecting rod mechanism comprise be mounted to wing flap around first axle arrange the first pivot and be attached to the first pivot, for the second pivot around the second axial-movement transverse to first axle.Connecting rod mechanism comprises at least one pivotal arm further, and the second axle is connected to sensor by it.First and second axle around the linear and rotary motion of the motor fitness wing flap of the axis of transverse direction, and by this motion UNICOM to sensor.
These and other feature that understanding that can be best from the following description and accompanying drawing is disclosed herein, following be briefly description.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the aircraft of the example comprising removable wing flap element.
Fig. 2 is the partial section of the wing of the example comprising removable wing flap and sensor module.
Fig. 3 is the partial cut away view of the sensor module of the example being attached to the removable wing flap being in retracted position.
Fig. 4 is the partial section that wing flap is in the sensor module of the example close to extended position.
Fig. 5 is the transparent view of the sensor module of the example being in retracted position.
Fig. 6 is the enlarged view of first and second pivot being attached to removable wing flap.
Fig. 7 is the section drawing of first and second pivot of the example being attached to removable wing flap.
Detailed description of the invention
With reference to Fig. 1 and 2, the aircraft 10 of example comprises the fixing wing 12 with moveable wing flap 14.Wing flap 14 is the example of moveable airfoil component, and it can move between the extended position shown in the retracted position shown in Fig. 1 and Fig. 2.Detect the motion of wing flap 14, and utilize sensor module 16 by the motion UNICOM of wing flap 14 to controller 22.Sensor module 16 detects the position of moveable wing flap 14, and by the position UNICOM of moveable wing flap 14 to controller 22.In this example, sensor module 16 comprises sensing device 18, and it produces the signal of the position of instruction wing flap 14, this signal is sent to controller 22, to confirm that wing flap 14 is in desired position.
The sensor module 16 of example comprises connecting rod mechanism 20, and it is attached to moveable wing flap 14.Connecting rod mechanism 20 mechanically by the motion UNICOM of wing flap 14 to sensing device 18.The motion of wing flap 14 when it moves to extended position from retracted position of example comprises linear component and rotational component simultaneously.Sensor module 16 adapts to this motion by connecting rod mechanism 20.The connecting rod mechanism 20 of example adapts to the total travel of the wing flap 14 between extended position and retracted position.And the sensor module 16 comprising connecting rod mechanism 20 of example is also comprised among the internal capacity of wing 12 of example.The sensing device 18 of example is mounted to the fixing structure 24 in wing 12, wherein connecting rod mechanism is attached to removable wing flap 14 at one end, and is attached to sensing device 18 at the second end place.
In continuation with reference to reference Fig. 3 and 4 while Fig. 2, the sensor module 16 of example comprises sensing device 18, and it is driven by connecting rod mechanism 20.Sensing device 18 comprises downward relative to the motion of wing flap 14 and vertically extending axle 26.By the rotation of sensing device 18 detecting sensor axle 26, and the rotation of sensor axis 26 is utilized to represent the position of wing flap 14.In this example, sensing device 18 comprises revolve inclination sensor, and it utilizes the inductance corresponding to the rotation of axle 26 to change, to determine the position of wing flap 14.This sensing device 18 can also be the Connector Clip of bear box, and bear box can comprise bearing with support link mechanism 20.It should be understood that known generation represents that other sensing devices of motor message are also among design of the present invention.
Linkage member 20 comprises the first pivotal arm 28, and it is at one end connected to sensor axis 26, is attached to the second pivotal arm 30 at the second end.Centrally-pivoted axle 32 is provided, the first arm 28 is connected to the second arm 30, relative to each other move around centrally-pivoted axle 32 to make the first arm 28 and the second arm 30.First arm 28 and the second arm 30 removable around centrally-pivoted axle 32 in almost parallel plane.Second arm 30 comprises spherical bearing 49 in the junction with centrally-pivoted axle 32, becomes possibility to make the second arm 30 relative to some motion of the plane of movement of the first arm 28.In this example, the first arm 28 and the second arm 30 move in the almost parallel plane of horizontal orientation.But, the concrete orientation of the first arm 28 and the second arm 30 can be revised, to adapt to the real needs applied.Second arm 30 extends to the second pivot 34 be installed in the first pivot 36.First pivot 36 and then be connected to wing flap 14.
The motion of the wing flap 14 of example starts along the rectilinear direction away from the retracted position shown in Fig. 3.When wing flap 14 is close to extended position (shown in Fig. 4), it starts to be rotated down.Being rotated down of wing flap 14 can not be adapted to by the parallel motion of the first arm 28 and the second arm 30.First pivot 36 and the second pivot 34 adapt to the rotary motion of wing flap 14, also adapt to the motion of translation of wing flap 14 simultaneously.
With reference to Fig. 5, the second arm 30 comprises gimbal attachment arrangement end, and it is attached to the second axle 34.The gimbal attachment arrangement end of example is used for the motion around two axis in junction.In this example, gimbal attachment arrangement end comprises forked end portions 42.Connection between forked end portions 42 and the second axle 34 is used for the relative motion around the second axis 40 of the second arm 30.In this example, the second axis 40 is directed transverse to first axle 38 ground, and the first axle 36 rotates around first axle 38.The pivoting action between forked end portions 42 is provided around the rotation of axis 40 by axle.And the connection between forked end portions 42 is used for the relative motion between axle 34 and forked end portions 42.The forked end portions 42 of example is not fixed to axle 34.In other words, forked end portions 42 and the second axle 34 is each all can move around the second axis 40 relative to the first axle 36.First axle 36 is attached to wing flap 14 by base 44.First axle 36 rotates around axis 38, and this axle 36 adapts to the rotary motion of wing flap 14 relative to the plane of movement of the first arm 28 and the second arm 30.
With reference to Fig. 6 and 7, the forked end portions 42 showing the second arm 30 is connected to the second axle 34.First axle 36 is supported in base 44, and base is fixed to wing flap 14.First axle 36 of example comprises thread head, and it receives nut 48, to be held in base 44 by the first axle 36.Due to the pivotal attachment provided by the first pivot 36, therefore wing flap 14 can rotate around axis 38 relative to the second arm 30.
First pivot 36 of example comprises along the Part I 56 of first axle 38 extension and transversely in the Part II 58 that Part I 56 extends with the second axis 40 of first axle 38.In this example, Part I 56 and Part II 58 form the integral features of the first pivot 36.Second axle 34 is installed on the chamber 54 be defined in Part II 58.Second pivot 34 is supported in the first axle 36, to provide the rotation around the second axis 38.Second axle 34 is remained on suitable position by the nut 46 be received on the second axle 34.Bearing 50 is arranged between axle 36 and base 44, to reduce friction, improves durability.Packing ring 52 is provided between axle 34 and forked end portions 42 further, and packing ring provides the friction of reduction and the antiwear characteristic of raising.
In operation, wing flap 14 starts from the retracted position shown in Fig. 3.In retracted position, the first pivotal arm 28 and the second pivotal arm 30 are folded each other.The motion of wing flap 14 starts from wing 12 linearly.First arm 28 and the second arm 30 relative to each other rotate around centrally-pivoted axle 32, to launch.The expansion campaign rotation sensor axle 26 of wall 28,30, its triggers sense device 18, to start to detect motion.The motion triggers of sensor axis 26 produces the signal being sent to controller 22.Further, motion of translation makes the first pivotal arm 28 and the second pivotal arm 30 extend and launch further.The rotation of the first arm 28 and the second arm 30 is adapted to by the second pivot 34 further.
When wing flap is close to complete extended position, it starts to be rotated down.First pivotal arm 28 and the second pivotal arm 30 while movement, also can adapt to the pivotable occurred together with the up-and-down movement of wing flap of the complete folded-out position at wing flap in the Part I process at flap kinematics in almost parallel plane.This motion is adapted to by the spherical bearing 49 of the first pivotal axis 36, second pivotal axis 34 be supported in base 44 and the connecting rod 30 that is arranged in centered pivot point 32.Therefore, the sensor module 16 of example is for the position of the motion of translation determination wing flap 14 of the extension by being coupled to rotary motion.In addition, the sensor module of example may be used for the application needing arbitrarily to measure any flight-control surfaces or removable panel, this flight-control surfaces or removable panel are included in the motion in more than one plane, such as aileron, alighting gear door, even for the THR REV of gas-turbine.
Although describe exemplary embodiment, those skilled in the art will recognize that, some amendment can in the scope of the present disclosure.Therefore, following claim be studied to determine scope of the present invention and content.
Claims (19)
1. for measuring a sensor module for the position of moveable airfoil component, it is characterized in that, described sensor module comprises:
First pivot, be attached to around first axle motion, described first pivot can be mounted to moveable airfoil component;
Second pivot, is attached to described first pivot, for around the second axial-movement transverse to described first axle;
At least one pivotal arm, it is attached to described second pivot; And
Sensor device, it comprises sensor axis, and described sensor axis is rotatable to provide the output signal of the position indicating described moveable airfoil component in response to the motion of at least one pivotal arm described.
2. sensor module according to claim 1, wherein, at least one pivotal arm described comprises the first pivotal arm being attached to the second pivotal arm, and described first pivotal arm is attached to described sensor axis pivotally, and described second pivotal arm is attached to described second pivot.
3. sensor module according to claim 2, wherein, described first pivotal arm and described second pivotal arm are attached to one another pivotally, to provide the relative motion in parallel plane.
4. sensor module according to claim 2, wherein, described first pivotal arm and described second pivotal arm are attached pivotally by spherical bearing, and described spherical bearing realizes the relative motion outside parallel plane of described first pivotal arm and the second pivotal arm.
5. sensor module according to claim 3, wherein, described first pivot around the motion of described first axle transverse to the motion of described first pivotal arm and described second pivotal arm.
6. sensor module according to claim 1, wherein, described first pivot realizes the rotation of described moveable airfoil component around described first axle.
7. sensor module according to claim 1, wherein, described sensor axis rotates around the axis transverse to described first axle.
8. sensor module according to claim 1, wherein, described first axle comprises the Part I and the Part II along described second Axis Extension that extend along described first axle, and described Part II comprises the inner chamber of the rotation supporting described second axle.
9. sensor module according to claim 8, wherein, described second axle is arranged in the described Part II of described first axle movably, rotates around described first axle to make described second axle together with the first pivot.
10. sensor module according to claim 1, wherein, described sensor axis extends vertically downward from described sensor device.
11. 1 kinds, for the wing flaps assembly of aircraft, is characterized in that, comprising:
Wing flap, it is removable relative to wing; And
Sensor module, for determining the position of described wing flap relative to described wing, described sensor module comprises:
First pivot, be attached to around first axle motion, described first pivot can be mounted to described wing flap;
Second pivot, is attached to described first pivot, for around the second axial-movement transverse to described first axle;
At least one pivotal arm, it is attached to described second pivot; And
Sensor device, it comprises sensor axis, and described sensor axis is rotatable to provide the output signal of the position indicating described wing flap in response to the motion of at least one pivotal arm described.
12. wing flaps assemblies according to claim 11, wherein, at least one pivotal arm described comprises the first pivotal arm being attached to the second pivotal arm, and described first pivotal arm is attached to described sensor axis pivotally, and described second pivotal arm is attached to described second pivot.
13. wing flaps assemblies according to claim 12, wherein, described first pivotal arm and described second pivotal arm are connected to each other pivotally, to provide the relative motion in parallel plane.
14. wing flaps assemblies according to claim 11, wherein, described wing flap around described first axle and described first pivot rotatable.
15. wing flaps assemblies according to claim 11, wherein, described sensor axis rotates around the axis transverse to described first axle, and extends vertically downward from described sensor device.
16. 1 kinds for determining the method for the position of wing flaps assembly, is characterized in that, comprising the following steps:
Limit the motion of wing flaps between retracted position and extended position, wherein, described wing flaps is rotated relative to motion of translation at described extended position place;
First pivot is mounted to described wing flaps around first axle, to make described wing flaps rotatable around described first axle;
Pivotal mounting to described first pivot by second, for rotating around the second axis transverse to described first axle;
At least one pivotal arm is connected to described second pivot, for by the motion UNICOM of described wing flaps to sensor device; And
In response to by least one pivotal arm UNICOM described to the motion of described sensor device, produce the output of the position representing described wing flaps.
17. methods according to claim 16, wherein, are connected to described second pivot and comprise the first pivotal arm is connected to described sensor device, and the second pivotal arm is connected to described first pivotal arm and described second pivot by least one pivotal arm.
18. methods according to claim 17, comprise and described first pivotal arm are connected to described second pivotal arm, for moving in parallel plane.
19. methods according to claim 17, comprise and install described sensor device, to make sensor axis relative to the motion vertical of described first pivotal arm and described second pivotal arm to downward-extension.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/150502 | 2011-06-01 | ||
| US13/150,502 US8438743B2 (en) | 2011-06-01 | 2011-06-01 | Resolver type skew sensor with gimbal attachment |
| US13/150,502 | 2011-06-01 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102806992A CN102806992A (en) | 2012-12-05 |
| CN102806992B true CN102806992B (en) | 2015-09-16 |
Family
ID=46229216
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210178028.5A Active CN102806992B (en) | 2011-06-01 | 2012-06-01 | There is the revolve inclination sensor of gimbal attachment arrangement |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US8438743B2 (en) |
| EP (1) | EP2530019A1 (en) |
| KR (1) | KR20120135051A (en) |
| CN (1) | CN102806992B (en) |
| CA (1) | CA2776427C (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103308023B (en) * | 2013-01-05 | 2016-03-30 | 中国航空工业集团公司西安飞机设计研究所 | A kind of angle displacement measuring device and measuring method |
| US9463869B2 (en) * | 2014-06-06 | 2016-10-11 | The Boeing Company | Slidable divergent trailing edge device |
| CN104121836B (en) * | 2014-06-27 | 2016-12-07 | 中航飞机股份有限公司西安飞机分公司 | A kind of aircraft flap trailing edge stagger measuring method and device |
| US10137999B2 (en) * | 2017-03-30 | 2018-11-27 | The Boeing Company | Methods and apparatus for detecting airflow control surface skew conditions |
| CN108945516A (en) * | 2018-07-27 | 2018-12-07 | 中国商用飞机有限责任公司 | Aircraft slat tilt detection device and its localization method |
| CN108945517A (en) * | 2018-07-27 | 2018-12-07 | 中国商用飞机有限责任公司 | Aircraft slat tilt detection device and its localization method |
| CN111731468B (en) * | 2019-04-12 | 2022-01-07 | 北京京东乾石科技有限公司 | Airfoil surface linkage device and aircraft |
| US20230159183A1 (en) * | 2021-11-19 | 2023-05-25 | The Boeing Company | Systems and methods for detecting a jam of a flap of a wing of an aircraft |
| CN114577254B (en) * | 2022-05-07 | 2022-09-09 | 成都凯天电子股份有限公司 | High-reliability detection method and system based on undercarriage inductive proximity sensor |
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2011
- 2011-06-01 US US13/150,502 patent/US8438743B2/en active Active
-
2012
- 2012-05-07 CA CA2776427A patent/CA2776427C/en active Active
- 2012-05-25 KR KR1020120056035A patent/KR20120135051A/en not_active Application Discontinuation
- 2012-05-30 EP EP12169998A patent/EP2530019A1/en not_active Withdrawn
- 2012-06-01 CN CN201210178028.5A patent/CN102806992B/en active Active
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| CN101346276A (en) * | 2005-12-29 | 2009-01-14 | 空中客车德国有限公司 | Airfoil for an aircraft and aircraft |
| CN102076559A (en) * | 2008-06-24 | 2011-05-25 | 伍德沃德Hrt公司 | Position sensing assembly |
| CN101596935A (en) * | 2009-06-01 | 2009-12-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airplane trailing edge flap retracting mechanism |
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Also Published As
| Publication number | Publication date |
|---|---|
| CA2776427A1 (en) | 2012-12-01 |
| KR20120135051A (en) | 2012-12-12 |
| CA2776427C (en) | 2013-11-12 |
| US20120304475A1 (en) | 2012-12-06 |
| US8438743B2 (en) | 2013-05-14 |
| CN102806992A (en) | 2012-12-05 |
| EP2530019A1 (en) | 2012-12-05 |
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